function [flight_cond]=f_condition(mgc)

% flight_cond: Array containing the flight and atmospheric conditions, listed bellow, at the main flight phases:
	%	The parameters are:
		% 1: Mach number .Mach
		% 2: Reynolds number .Re
		% 3: Reference altitude .alt
		% 4: Reference pressure .p
		% 5: Reference temperature .oat
		% 6: Reference viscosity .mu
		% 7: Reference density .rho
		% 8: True air speed .tas
		
	% The flight conditions are:
		% 1: Take off .to
		% 2: Climb .climb
		% 3: Cruise .cruise
		% 4: Descent .desct
		% 5: Loiter .loi
		% 6: Landing .lndg
	% Example: flight_cond.cruise.mach
    %
% 	 If the Reynolds number and atmosphere parameters provided are equal
% 	 to 0, its value is computed from the givem conditions at the ISA
%     The minimal parameters are:
%             -Mach/tas >  .Mach/.tas
%             -altitude >  .alt
%       If both .Mach and .tas fields contain non zero values, the Mach will
%       be considered and the true air speed will be computed
    
    
    flight_cond.to.Mach=0.2;
    flight_cond.to.Re=0;
    flight_cond.to.alt=20000;
    flight_cond.to.p=0;
    flight_cond.to.oat=0;
    flight_cond.to.mu=0;
    flight_cond.to.rho=0;
    flight_cond.to.tas=0;

    
    f_cond_aux=flight_cond.to;
    flight_cond.to=fill_f_cond(f_cond_aux,mgc);
    
    
    
    
    flight_cond.climb.Mach=0.2;
    flight_cond.climb.Re=0;
    flight_cond.climb.alt=20000;
    flight_cond.climb.p=0;
    flight_cond.climb.oat=0;
    flight_cond.climb.mu=0;
    flight_cond.climb.rho=0;
    flight_cond.climb.tas=0;
    
    f_cond_aux=flight_cond.climb;
    flight_cond.climb=fill_f_cond(f_cond_aux,mgc);
    
    
    
    
    flight_cond.cruise.Mach=0.2;
    flight_cond.cruise.Re=0;
    flight_cond.cruise.alt=20000;
    flight_cond.cruise.p=0;
    flight_cond.cruise.oat=0;
    flight_cond.cruise.mu=0;
    flight_cond.cruise.rho=0;
    flight_cond.cruise.tas=0;
    
    f_cond_aux=flight_cond.cruise;
    flight_cond.cruise=fill_f_cond(f_cond_aux,mgc);
    
    
    
    flight_cond.desct.Mach=0.2;
    flight_cond.desct.Re=0;
    flight_cond.desct.alt=20000;
    flight_cond.desct.p=0;
    flight_cond.desct.oat=0;
    flight_cond.desct.mu=0;
    flight_cond.desct.rho=0;
    flight_cond.desct.tas=0;
    
    f_cond_aux=flight_cond.desct;
    flight_cond.desct=fill_f_cond(f_cond_aux,mgc);
    
    
    
    flight_cond.loi.Mach=0.2;
    flight_cond.loi.Re=0;
    flight_cond.loi.alt=20000;
    flight_cond.loi.p=0;
    flight_cond.loi.oat=0;
    flight_cond.loi.mu=0;
    flight_cond.loi.rho=0;
    flight_cond.loi.tas=0;
    
    f_cond_aux=flight_cond.loi;
    flight_cond.loi=fill_f_cond(f_cond_aux,mgc);
    
    
    flight_cond.lndg.Mach=0.2;
    flight_cond.lndg.Re=0;
    flight_cond.lndg.alt=20000;
    flight_cond.lndg.p=0;
    flight_cond.lndg.oat=0;
    flight_cond.lndg.mu=0;
    flight_cond.lndg.rho=0;
    flight_cond.lndg.tas=0;
    
    f_cond_aux=flight_cond.lndg;
    flight_cond.lndg=fill_f_cond(f_cond_aux,mgc);
    
    
    
    
    
    
    
    
    
    
    
    
    
    
    